NUMERICAL PREDICTION OF VORTICAL FLOW OVER SLENDER DELTA-WINGS

被引：10

作者：

EKATERINARIS, JA

SCHIFF, LB

机构：

[1] NASA Ames Research Center, Moffett Field, CA

来源：

JOURNAL OF AIRCRAFT | 1993年 / 30卷 / 06期

关键词：

D O I：

10.2514/3.46437

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Three-dimensional Navier-Stokes numerical simulations are necessary to correctly predict the complex leeward-side flow characteristics over delta wings, including leading-edge separation, secondary separation, and vortex breakdown. This article presents Navier-Stokes solutions of subsonic vortical flow over a 75-deg sweep delta wing with a sharp leading edge. The sensitivity of the solution to the numerical scheme is examined using both a partially upwind scheme and a central-differencing scheme. The effect of numerical grid density is also investigated. An embedded grid approach is implemented to enable higher resolution in selected isolated flow regions, such as the leeward-side surface flow region, and the leading-edge vortical now region.

引用

页码：935 / 942

页数：8

共 22 条

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